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Full text of "XB-52 Stratofortress Standard Aircraft Characteristics 6 October 1950"

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SEC R --Er T experimental 






BY AUTHORITY OF 
COMMANDING GENERAL 
AIR MATERIEL COMMAND 
U. S. AIR FORCE 





Boeing 



EIGHT J57-P-( ) 

PRATT ft WHITNEY 



6 OCTOBER 1950 



S E C R. E T 



XB-52 



EXPERIMENTAL 



S^r ^ a*. ■ n f~ T 




Wing Area 4000 sq ft Wing Section: 

Aspect Ratio 8. 55 Root BAC 233 

MAC 275.5" ... .25b/2BAC248 

... . 45 b/2 BAC 235 
1000 gal 2140 gal Tip BAC 236 

8 gal 

8 gal 

2230 gal 

5 800 gal 

8 gal - ] ' / 

5540 gal 

" "il 

5400 gal 

5 370 gal 

2710 gal ^%*** 

8 gal y~ 2230 gal 
gal 

s 

2140 gal 

II ZLJL 8 gal 

8 gal 1000 S al 

Pressurized Area 
Fuel CUD ATO Oxidizer (MHOH 





XB-52 



Sr- *r 
c \j n t i 



6 OCTOBER 1950 



SECRET 



EXPERIMENTAL 



The XB-52 is a long range, high altitude, highspeed, heavy bomb- 
er designed for the destruction of surface targets. 

The normal crew of five (5) consists of: Pilot; Co-Pilot-Flight Eng- 
ineer; (2) Bombardier-Navigator- Weaponiers; Gunner-Radio Opera- 
tor. 

This aircraft resembles the B-47 and is equipped with a quadri- 
cycle main gear and wing-tip protecting gear. Automatic cabin pres- 
surization and conditioning is provided for all operations. A liquid 
oxygen system is provided for crew use. The tail contains provisions 
for liquid rocket assisted take-off and a deceleration parachute. Con- 
trol throughout the speed range from limit dive speed to landing speed, 
is obtained by using spoilers, ailerons, and flaps on the wing, a mov- 
able horizontal stabilizer, and conventional tail surfaces. The spoil- 
ers may also be used as airbrakes permitting descent from 55,000 feet 
to sea level at end of mission in approximately three minutes with gear 
down. 

The XB-52 passed through 4 preliminary design stages before the 
present configuration was decided upon as shown in the following table: 



Date Boeing Model No. Gross Wt. Power Plant 

(lb) 

28Junl946 462 360,000 (6) T35-1 

7 Jan 1947 464-22 480,000 (4) T35-3 

8 Dec 1947 464-35 280,000 (4) T35-5 

27 Oct 1948 464-49 330,000 (8) YJ57-P-3 

29 Mar 1950 464-67 390,000 (8) XJ57-P-1 

6 Oct 1950 464-67 390, 000 ( W/O ATO) (8)J57-P-(?) 

Current development is as follows: 

Present Design Initiated: 27 Oct 1948 

Mock-up Inspection: 26 Apr 1949 

Engine Nacelle Mock-up Inspection: 14 Jun 1950 

First Flight (1st article): Oct 1951 (est) 

First Flight (2nd article): Dec 1951 (est) 



POWER PLANT 

The first and second aircraft 
will be powered with (8) YJ57-P-3 
engines (8700 lb max thrust/SLS). 
These engines will subsequently be 
modified to give the following thrust 
ratings: MAX and MILITARY, 9250 
lb (with variable area nozzle) and 
9000 lb (with fixed area nozzle); 
NORMAL, 8700 lb. These ratings 
were used for performance shown 
in this chart, however, the model 
designation for this modified engine 
is undetermined. Further plans 
call for the addition of water injec- 
tion and overspeed to increase take- 
off thrust. Consideration of future 
addition of a short type take-off 
afterburner is dependent upon effect 
on fuel specifics. 

Liquid ATO used for perfor- 
mance is 30, 000 lb thrust for 60 
seconds. This will be reduced to 
20, 000 lb thrust ATO when water 
injection becomes available. 

BOMBS 

No. Size Type 

1 25, 000* T-28E2 

1 22, 000* T-40 

1 13, 000* VB-13 

1 12, 000* W-109 

8 2000 G. P. 

12 1000 G. P. 

16 500 G. P. 

*Space provisions only 
Note: Overall dimensions of the ir- 
regular shaped bomb bay are 
6'x6'x27' (approx.) 

DIMENSIONS 



Wing 

Span 185. 0' 

Incidence (root) ' 6° 

Dihedral (Chord plane) 2°30' 

Sweepback (L. E.) 36°54' 

Length . 152. 7' 

Height 48. 25' 

Tread (outrigger) 148. 9' 

Tread (main gear) 11.4' 



GUNS 

No. Cal. Rds. ea. Location 
2 . 50 . . . 600 Tail tur. 



CAMERAS 



(alternate installations) 
No. Type Lens 

1 . . . K-17C 6", 12"or 24" 

1 . . . K-22A 6"', 12" or 24" 

1 K-37 12" 

1 . . . K-38 24" or 36" 



WEIGHTS 



Loading Lb L. F. 

Empty 155, 200(E) 

Basic 156, 700(E) 

Design 390, 000 

Combat *256, 800 

Max T. O. ... t390, 000 2. 

Max Land . . . 270, 000 

(E) Estimated 
* For Basic Mission 
T Limited by strength (W/O expend- 
able weight of liquid ATO) 



FUEL 



Location No. Tanks Gal 

Wg* 4 9880 

Wg 3 9820 

Fus* 3 16, 570 

Wg, drop 2 . . 2000 

*Self-sealing Total 38,270** 

**Includes ATO fuel 

Grade JP-3 or 100/130. 

OIL 

Capacity (gal) 64 

Grade 1010 



ELECTRONICS 

UHF Command AN/ARC-27 

Liaison AN/ARC-25A 

Interphone USAF Combat 

Bombing-Navig. Radar K-1A 

Lor an AN/APN-9A 

IFF AN/APX-6 

Fire Control System A- 3 

Glide Path AN/ARN-5B 

Omni-Direct. Recvr . . . AN/ARN-14 

ECM +AN/APQ-27 

Radar Beacon *AN/APN-12 



♦Space provisions only 



6 OCTOBER 1950 



S E C R E T 



XB-52 3 



EXPERIMENTAL 



S^E C R E. T 



C ONDITIONS 



BASIC 
MISSION 



6000 LB BOMB 
MISSION 



TAKE-OFF WEIGHT ® 
Fuel at 6.0 lb/gal(grade 100/130) 
Military load (Bombs) 
Wing loading 

Stall speed(power off, land, conf ig. ) 
Take-off ground run at SL ® 
Take-off ground run with ATO ® 
Take-off to clear 50 ft ® 
Take-off to clear 50 ft with ATO ® 
Rate of climb at SL © 
Time: SL to 30,000 ft © 
Time: SL to 37, 000 ft © 
Service ceiling (100 fpm) © 
Service ceiling (one engine out) 

COMBAT RANGE © 
Average speed 
Initial cruising altitude 
Final cruising altitude 
Total mission time 

COMBAT RADIUS ® 
Average speed 
Initial cruising altitude 
Bombing altitude 

Bomb run speed ® 
Final cruising altitude 
Total mission time 



(lb) 
(lb) 
(lb) 
(lb/sqft) 
(kn) 



© 



(ft) 
(ft) 
(ft) 

D (") 

(fpm) 
(min) 
(min) 
(ft) 
(ft) 
(n. mi. ) 
(kn) 
(ft) 
(ft) 
(hr) 
(n. mi. ) 
(kn) 

(ft) 
(ft) 
(kn) 
(ft) 
(hr) 



I 

390, 000 
219, 240 
10, 000 
97. 5 
127. 
7820 
4720 
9700 
6220 
2400 
17. 5 
26. 
39, 500 

© 
6095 
454 
37,000 
51, 100 
13. 4 
3070 
451 
37,000 
46,500 

480 
52, 300 
13. 6 



II 

390, 000 
223, 398 
6000 
97. 5 
127.0 
7820 
4720 
9700 
6220 
2400 
17. 5 
26. 
39, 500 

© 

6265 

454 
37, 000 
50, 900 

13. 85 

3140 

452 
37, 000 
46, 500 

480 
52, 100 

13. 9 



COMBAT WEIGHT ®~ (lb) 

Combat altitude (ft) 

Combat speed ® (kn) 

Combat climb ® (fpm) 

Combat ceiling (500 fpm) ® (ft) 

Service ceiling (100 fpm) ® (ft) 

Service ceiling (one engine out) (ft) 

Max rate of climb at SL ® (fpm) 

Max speed at 20, 000 ft ® (kn) 

LANDING WEIGHT (lb) 

Ground roll at SL (ft) 

Ground roll (auxiliary brake) © (ft) 

Total from 50 ft (ft) 

Total from 50 ft (auxiliary brake) © (ft) 



256, 800 
35, 000 

516 

2150 
46,500 
49,900 

© 
4550 
531 
180, 300 
2100 
1550 
2900 
2300 



259, 000 
46, 300 

491 

300 
46, 300 
49, 500 

© 
4550 
531 
181, 000 
2100 
1550 
2900 
2300 



NOTES: 
© Max power 

S Normal power 
Detailed descriptions of RADIUS & 
RANGE missions are given on page 6. 



® For Radius Mission is radius is shown liquid ATO amouting to approximately 15, 000 lb of oxidizer and gas. 



Data not available 

With 30, 000 lb thrust ATO(60 sec. ) 

With drag chute 

Does not include expendable weight of 



PERFORMANCE BASIS: 

(a) Data source: Estimates 

(b) Performance is based on powers shown on page 6. 



XB-52 



S E C R E T 



6 OCTOBER 1950 



S E C • R E T 



EXPERIMENTAL 




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FORMAL POWER 






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400 440 480 520 

KNOTS 



560 




C/J 

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520 



500 



480 



460 



440 











II 1 1 












500 NAUTICAL MILE 
COMBAT ZONE 


































































































































1 


6000 


LB BOMB LOAD| \ 















































































































2800 3000 3200 

NAUTICAL MILES 



6 OCTOBER 1950 



XB-52 



EXPERIMENTAL 



NOTES 



FORMULA: RADIUS MISSION I 

Take-off, climb on course to 37,000 ft. altitude at aircraft speed 
for maximum rate of climb, cruise out at long range speeds increasing 
altitude with decreasing aircraft weigiit, make normal power bomb- 
runto target, conduct 6 minute normal power bomb-run, drop bombs, 
conduct normal power evasive action for 6 minutes, start cruise to 
home base at 46,500 ft. alt. arriving over home base at 52,300 ft. 
altitude. Range free allowances are: 5 minutes normal power fuel con- 
sumption for starting engines and take-off , plus 6 minutes normal pow- 
er evasive action, plus 10% of initial fuel for reserve. 

FORMULA: RANGE MISSION I 

Same as outbound leg of the Basic Radius formula continued with- 
out dropping the bombs until 90% of the initial fuel has been used at 
51,100 ft. alt., leaving 10% fuel reserve for combat, evasive action, 
landing reserve, or other considerations for which no distance credit 
is allowed. 

FORMULA: RADIUS MISSION II 

Same as the Basic Radius formula except 10,000 lb bomb is re- 
placed by 6, 000 lb bomb and additional fuel. Altitude at end of mis- 



sion is 52, 100 ft. 

FORMULA: RANGE MISSION II 

Same as Basic Range formula except 10, 000 lb bomb is replaced 
with6, 000 lb bomb and additional fuel. Altitude at the end of the mis- 
sion if 50, 900 ft. 

GENERAL DATA 

(a) Data is based on estimates. 

(b) Power values used in performance calculations are as follows: 



(8) J57-P- ( ) 


S. L. Static 


LB 


RPM 


Max: 


*9250 




Nor: 


8600 






*With variable area nozzle 





2L o 

a 



3" 
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O 
3 



01 c 

tfl (A 

^ 3 



XB~52 SECRET 6 OCTOBER 1950 

6